payload design criteria for the space test program standard interface vehicle (stp-siv)

Payload Design Criteria for the Space Test Program

Standard Interface Vehicle(STP-SIV)

Mr. Mike MarlowSTP-SIV Program Manager




National Science Foundation Workshop on Small SatelliteMissions for Space Weather and Atmospheric Research


National Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric ResearchNational Science Foundation Workshop on Small Satellite Missions for Space Weather and Atmospheric Research 22

PurposePurpose

Mission Capabilities Of The STP-SIV Spacecraft Standard Spacecraft To Payload Interfaces

Top-level Detail To Determine If STP-SIV Is A Candidate For Your Mission

Mission Capabilities Of The STP-SIV Spacecraft Standard Spacecraft To Payload Interfaces

Top-level Detail To Determine If STP-SIV Is A Candidate For Your Mission


STP-SIV Road MapSTP-SIV Road Map2005 2007 2009 2011 2013

SERB Payload AnalysisConcept Definition

Requirements DefinitionIndustry Briefings

Source Selection Documentation

SIV Delivery Order #1 (STPSat-2)Payload, LV Determination

S/C and S/V Development & Test

Source Selection

DO#2 (STPSat-3)

DO#3 (STPSat-4)

1 Apr 06

1 Apr 12

Last Order Date

DO#4 (STPSat-5)

DO# 2 buy long leads at ATPDO# 3 long leads on shelfDO#4 S/C Pre-assembled


Spacecraft CapabilitySpacecraft Capability

Orbit Altitude 400 – 850 km Orbit Inclination 0° – 98.8° Launch Mass ≤ 180 kg (ESPA driven)SV Stored Volume (cm) 60.9 x 71.1 x 96.5 (ESPA driven)Reliability (at 7 months) 0.90Stabilization Method 3-axisPointing Modes Nadir, Sun Pointing, SafeAttitude Knowledge 0.03° 3σ (goal 0.02° 3σ)Attitude Control 0.1° 3σ (goal 0.03° 3σ)Bus Voltage 28 V ±6Comm Frequency SGLSCommand Rate 2 kbps uplinkTelemetry Rate 2 Mbps downlinkData Storage 8 GbitsPayload Volume 0.14m3

Payload Mass 60 kg

Orbit Altitude 400 – 850 km Orbit Inclination 0° – 98.8° Launch Mass ≤ 180 kg (ESPA driven)SV Stored Volume (cm) 60.9 x 71.1 x 96.5 (ESPA driven)Reliability (at 7 months) 0.90Stabilization Method 3-axisPointing Modes Nadir, Sun Pointing, SafeAttitude Knowledge 0.03° 3σ (goal 0.02° 3σ)Attitude Control 0.1° 3σ (goal 0.03° 3σ)Bus Voltage 28 V ±6Comm Frequency SGLSCommand Rate 2 kbps uplinkTelemetry Rate 2 Mbps downlinkData Storage 8 GbitsPayload Volume 0.14m3

Payload Mass 60 kg+X

+Z

+Y


Launch Vehicle CompatibilityLaunch Vehicle Compatibility

Minotaur IMinotaur IV

EELV Secondary Payload Adaptor (ESPA)[Atlas and Delta]

Falcon 1 Pegasus/Raptor


Spacecraft DesignSpacecraft Design

Z

X Y

1 Star Tracker, 1 magnetometer6 sun sensors, 1 GPS receiver, 3 reaction wheels, 3 torque rods

2 fixed/deployed arrays 1 gimbaled arrayGaAs UTJ solar cells30 A-hr Li Ion battery

Payload Interface Panel

Star tracker

Payload Volume

Silver Teflon Coated Radiator

Rigid LV Interface Panel

Sample Payload Configurations


Topside Sounder Concept on STP-SIVTopside Sounder Concept on STP-SIV

Configuration above shows four deployed 4-m antennas on all four corners of the STP-SIV spacecraft

This effectively yields two, crossed 8-m dipole antennas

Configuration above shows four deployed 4-m antennas on all four corners of the STP-SIV spacecraft

This effectively yields two, crossed 8-m dipole antennas


Spacecraft to Payload InterfacesSpacecraft to Payload Interfaces

Mechanical

Thermal

Data

Power

EMI

• 100 Watts Orbit Average• 28 V ±6

• Case by Case• System Test on each mission

• 1” grid aluminum panel• #10 fasteners • Stringent environment • Coupled Heat Transfer

• Plate temperatures: -20o to +50o C• 100 Watts Heat Rejection

• Up to 2 Mbps data rate• RS-422 Command and Telemetry• Synchronous data transmission• 8 Bi-Level Discreet I/O channels• 8 analog channels/payload


Feasibility Study Feasibility Study

Payload to spacecraft compatibility

Payload to payload compatibility

Identifies potential risks

ROM estimate to integrate, test and operate

Payload to spacecraft compatibility

Payload to payload compatibility

Identifies potential risks

ROM estimate to integrate, test and operate


OpportunitiesOpportunities

Enables space weather communities to leverage S&T spaceflight opportunities Share SIV payload space Rideshare S&T launch opportunities

ESPA on every EELV, payload adaptors on Minotaurs I & IV

Provides cost-effective platform to demo payloads and systems to support space weather programs

Basis for follow-on programs Larger spacecraft class Use of spacecraft to payload “standard” interfaces

Enables space weather communities to leverage S&T spaceflight opportunities Share SIV payload space Rideshare S&T launch opportunities

ESPA on every EELV, payload adaptors on Minotaurs I & IV

Provides cost-effective platform to demo payloads and systems to support space weather programs

Basis for follow-on programs Larger spacecraft class Use of spacecraft to payload “standard” interfaces


SummarySummary

SIV is a change from past STP business practices Moving away from “one-of-a-kind” spacecraft to gain

benefits of successive spacecraft builds More responsive IDIQ contract, fits with other Space

Development & Test Wing IDIQs

Planned to provide improved access to space for SERB S&T payloads

Potential benefits for broader space community

SIV is a change from past STP business practices Moving away from “one-of-a-kind” spacecraft to gain

benefits of successive spacecraft builds More responsive IDIQ contract, fits with other Space

Development & Test Wing IDIQs

Planned to provide improved access to space for SERB S&T payloads

Potential benefits for broader space community


Standard Payload to Spacecraft Interfaces Standard Payload to Spacecraft Interfaces

Mechanical Fasten payload hardware to

spacecraft structure Align payload hardware to

spacecraft reference

Thermal Sense temperature at payload to

spacecraft interface Control temperature at payload

to spacecraft interface by affecting spacecraft side

Mechanical Fasten payload hardware to

spacecraft structure Align payload hardware to

spacecraft reference

Thermal Sense temperature at payload to

spacecraft interface Control temperature at payload

to spacecraft interface by affecting spacecraft side

Payload

1

Payload

2

Spacecraft

M

T

P

D

Power Supply primary main electrical

power to payload Supply redundant main payload

power Supply power for payload heaters

Data Supply bilevel discrete signal from

spacecraft to payload for reset or other switching functions

Provide command data from spacecraft to payload

Provide data transfer from spacecraft to payload (code upload, time synch, attitude, GPS)

Provide digital telemetry data from payload to spacecraft

Provide analog data from payload to spacecraft (state of health monitoring)


STP Rideshare OpportunitiesSTP Rideshare Opportunities

FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY131Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q 1Q 2Q 3Q 4Q

FY09 Minotaur IVPL SelectionDevelopmentMission IntegrLaunch

DMSP F-19SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch

STP-2SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch

FY11 MinotaurPL SelectionMission IntegrLaunch

DMSP F-20SPL SelectionSpecial Studies*Mission UniqueMission IntegrLaunch

FY13 MinotaurPL SelectionMission IntegrLaunch

Apr 08

Oct 08

Oct 10

Oct 05

Jan 06

Apr 06

There are potentially 30 ESPA-class spacecraft rideshare opportunities

between FY09 – FY13

payload design criteria for the space test program standard interface vehicle (stp-siv)

Documents

mission briefingsummarysiv

payload adaptors

stpsiv spacecraftthis

oneofakind spacecraft

space weather programs

payload interfacestoplevel

case system test

small satellitemissions